Ramped dovetail rails for rotor blade assembly

ABSTRACT

A fan blade (34) of a gas turbine engine (10) includes a pair of root rails (54) disposed on a bottom (56) of a dovetail root portion (44) thereof. The pair of root rails (54) has a wedge-shaped contour and is tapered in a decreasing cross-section from the leading edge (50) to the trailing edge (52). The root rails (54) provide a wide, stable base for the blade to minimize tangential motion during windmilling. A pair of slot rails (76) is provided on the base (70) of a dovetail-shaped slot (40) retaining the dovetail root portion (44) of the blade (34). The slot rails (76) of the dovetail slot (40) mate with the root rails (54) of the dovetail root portion (44).

This is a request for filing a Continuation application under 37 CFR1.62 of application Ser. No. 08/236,717 filed on Apr. 29, 1994, now U.S.Pat. No. 5,431,542.

TECHNICAL FIELD

This invention relates to gas turbine engines and, more particularly, torotor blades therefor.

BACKGROUND OF THE INVENTION

A widely used type of a gas turbine engine is a turbofan. Thedistinguishing feature of the turbofan is an axial flow fan disposed inthe forward portion of the engine within an open duct. The fan isequipped with rotating blades and stationary vanes. Each fan bladecomprises an airfoil portion and a dovetail-shaped root portion securedin a fan disk. The fan disk includes a plurality of dovetail-shapedslots disposed circumferentially therein to engage the dovetail rootportion of the blades. The disk and the blades are typicallymanufactured from a metal alloy.

Windmilling is one of many conditions to which the gas turbine engine issubjected, having adverse consequences. During windmilling, which occurswhen the aircraft is parked on the ground with its engine shut down,wind enters the forward or aft portion of the engine and impartstangential (with respect to the disk) motion to the fan assembly,thereby subjecting the fan blades to rocking motion within the diskslots. As the fan blades and disk rotate, a gravitational force tends topull each blade reciprocally in opposite tangential direction dependingupon which side of the engine the blade is disposed. As the bladesreciprocate tangentially due to windmilling, they rock from one side ofthe slot to the opposite side of the slot banging against the oppositeside of the slot. Such repetitive impact causes abrasion on the disk andthe blades. Although both the disk and the blades are coated with anantigallant coating, both the disk and the blades are nonethelessdamaged gradually over extended periods of time.

Although the top portion of the dovetail root portion experiences themost damage due to additional wear caused by the centrifugal loadingduring operation of the engine, the bottom of the dovetail portion alsobecomes worn. The problem of abrasion on the bottom of the dovetail isexacerbated by the location of vent openings thereon, which arecharacteristic of and necessary for the manufacture of hollow fanblades. Furthermore, the vent openings must be sealed to preventpotential contaminants, such as sand, dust, or oil, from entering intointernal cavities of the blade. The sealants used to close the ventopenings must also be protected from abrasion due to motion of theblades within the slot.

The worn blades and disks either must be repaired periodically orreplaced if damage is beyond repair. Both alternatives are costly. Theproblem of tangential motion in fan blades during windmilling isparticularly acute in modern blades that do not include mid-spanshrouds. The mid-span shrouds tend to provide structural support and tohold blades separated and in an upright position.

U.S. Pat. No. Re 33, 954 entitled "Rotor Blade Assembly" issued to Hondaet al and assigned to United Technologies Corporation discloses a fanassembly having a single wedge-shaped protrusion extending outwardlyfrom the base of each disk slot and a tapered surface at the bottom ofthe root section of the corresponding blade. Although the arrangementfacilitates improved disassembly of blades from the disk, it does notminimize the above noted reciprocating tangential motion of the bladesduring windmilling.

During operation of the engine, the disk experiences extreme stresses,including a circumferential (hoop) stress. The circumferential stressfield in the disk is a substantially circular, continuous fieldoccurring in a "live rim", which is defined as a continuous outercontour within the disk, without any interruptions. The circumferentialstress is particularly undesirable if it occurs in locations such as theabove-noted wedge-shaped protrusions at the bottoms of the disk slots.

Thus, there is a need to minimize damage to fan blades and to the diskthat may be caused by the reciprocating tangential motion of the fanblades within the disk slots without a weight penalty. Additionally, itis necessary to reduce hoop stress proximal to the bottoms of the diskslots.

DISCLOSURE OF THE INVENTION

According to the present invention, a pair of root rails is provided onthe bottom of a dovetail-shaped root portion of a gas turbine engineblade to minimize reciprocating tangential motion of the blades withindovetail-shaped slots in which the root portions of the blades areretained. Each root rail is wedge-shaped, tapering in a decreasingcross-section from the leading edge to the trailing edge of the blade.The root rails provide a wide, stable base for the blade and thusminimizes reciprocating tangential motion of the blade within the slotduring windmilling. A root groove formed between the root rails,minimizes the weight of the blade and protects a plurality of ventopenings formed therein as well as a sealant for the vent openings, frombeing abraded during tangential motion of the blade within the slot.

According to an aspect of the present invention, a pair of slot rails onthe base of the disk slot mates with the blade root rails. Each slotrail is wedge-shaped and tapers oppositely to the corresponding bladeroot rail. A slot groove, defined between the pair of the slot rails,moves the circumferential stress radially inwardly from the outer edgesof the slot rails, thus improving fatigue life of the disk.

The foregoing and other advantages of the present invention become moreapparent in light of the following detailed description of the exemplaryembodiments thereof, as illustrated in the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a simplified, partially sectioned view of a gas turbine engineof the type employing a rotor blade assembly of the present invention;

FIG. 2 is an enlarged, exploded top perspective view of a fan bladehaving a pair of root rails thereon and a fan disk having a pair of slotrails thereon, according to the present invention;

FIG. 3 is an enlarged front, cross-sectional view of the portion of thefan blade and the fan disk of FIG. 2; and

FIG. 4 is a fragmentary cross-sectional view taken in the direction ofline 4--4 of FIG. 3.

BEST MODE FOR CARRYING OUT THE INVENTION

Referring to FIG. 1, a gas turbine engine 10 includes a fan section 12,a compressor 14, a combustor 16, and a turbine 18. Air 20 flows axiallythrough the sections 12-18 of the engine 10. The fan 12 accelerates theair to contribute to the overall thrust produced by the engine. As iswell known in the art, the air 20, compressed in the compressor 14, ismixed with fuel which is burnt in the combustor 16 and expanded in theturbine 18, thereby rotating the turbine 18 and driving the fan 12 andthe compressor 14.

The fan section 12 includes a fan disk 32 and a plurality of fan blades34 within an open duct 36. The disk 32 includes a plurality of dovetailslots 40 formed within the outer circumference of the disk to retain thefan blades 34, as shown in FIG. 2.

Each fan blade 34 comprises an airfoil-shaped portion 42 and adovetail-shaped root portion 44. The airfoil-shaped portion 42 includesa concave wall 46 and a convex wall 48 extending in a chordwisedirection from a leading edge 50 to a trailing edge 52. Thedovetail-shaped root portion 44 includes a pair of wedge-shaped rootrails 54 extending from a bottom 56 of the dovetail-shaped root portion44. The root rails 54 are tapered in decreasing cross-section from theleading edge 50 to the trailing edge 52 of the blade 34. The pair of theroot rails 54 define a root groove 58 therebetween. The blade 34includes a hollow cavity 60 therein, as shown in FIG. 3. A plurality ofvent openings 62 (necessary for manufacturing reasons) are formed withinthe dovetail-shaped root portion 44, providing communication between thecavity 60 and the root groove 58 on the bottom 56 of the dovetail rootportion 44. A sealant 64, disposed within the root groove 58 over theopening 62, is used to close the opening 62 and to prevent contaminantsfrom entering the hollow cavity 60.

Each dovetail slot 40 includes a base 70 and extends from a front side72 to a rear side 74 of the disk 32, so that when the slot 40 fullyengages the dovetail root 44 of the blade 34, the leading edge 50 of theblade 34 is aligned with the front side 72 of the disk 32 and thetrailing edge 52 of the blade 34 is aligned with the rear side 74 of thedisk 32, as best shown in FIG. 4. A pair of wedge-shaped slot rails 76extends from the base 70 of the slot 40. The slot rails 76 are taperedto mate with the root rails 54. Thus, the cross-section of the slotrails 76 increases from the front side 72 to the rear side 74,oppositely from the taper of the root rails 54. The slot rails define aslot groove 78 therebetween.

During operation of the engine 10, the disk 32 experiences extremestresses, including high circumferential (hoop) stress in the area atouter edges 80 of the slot rails 76. The slot groove 78 between the pairof slot rails 76 causes an interruption within the disk 32 and thereforerelocates the hoop stress radially inwardly of the slot base. Thus, thegroove 78, by relocating the circumferential stress radially inwardly ofthe high stress concentration area at the outer edges 80 of the slotrails 76, improves the fatigue life of the disk 32 and enables the disk32 to tolerate more cycles than a disk without the slot groove 78 would.

During windmilling, a condition occurring when the aircraft is parked onthe ground with its engine shut down, the wind enters the forward or aftportion of the engine and imparts tangential (with respect to the disk32) motion to the fan 12. As the fan 12 rotates, gravitational forcestend to pull each blade 34 reciprocally in opposite tangential directiondepending on which side of the engine the blade is disposed. The pair ofroot rails 54 minimizes reciprocating tangential rocking motion of theblades 34 due to the readjustment within the slots 40 by providing awider and more stable base. The root groove 58 minimizes the overallweight of the blade 34 by eliminating material therefrom and shields theopenings 62 and the sealant 64 from abrasion against the slot 40 duringoperation in windmilling of the engine.

Although the invention has been shown and described with respect toexemplary embodiments thereof, it should be understood by those skilledin the art that various changes, omissions, and additions may be madethereto, without departing from the spirit and scope of the invention.For example, these concepts may be used on blades other than fan and arenot limited to fan blade applications.

What is claimed:
 1. A blade for use in a gas turbine engine, said bladehaving an airfoil portion and a dovetail root portion integrallyattached to said airfoil portion said airfoil portion having a leadingedge and a trailing edge, said blade characterized by:a pair of rootrails disposed on and integral with a bottom of said dovetail rootportion of said blade to minimize motion of said blade duringwindmilling; and a root groove defined between said root rails.
 2. Theblade according to claim 1 characterized by said pair of root railshaving a wedge-shaped contour, said pair of root rails being tapered ina direction of decreasing cross-section from said leading edge to saidtrailing edge of said blade.
 3. The blade according to claim 1 or 2characterized by a plurality of vent openings disposed within said rootgroove.
 4. A fan for use in a gas turbine engine having a plurality offan blades and a fan disk with a plurality of dovetail slots to receivesaid plurality of fan blades, each said fan blade having an airfoilportion and a dovetail root portion integrally attached to said airfoilportion, said airfoil portion having a leading edge and a trailing edge,said fan disk having a front side corresponding to said leading edge ofsaid blade and a rear side corresponding to said trailing edge of saidblade, said dovetail root portion retained within said dovetail slot,said fan characterized by:a pair of root rails, disposed on and integralwith a bottom of said dovetail root portion of said blade to minimizesaid blade motion during windmilling; and a pair of slot rails disposedon and integral with a base of said dovetail slot, said pair of slotrails mating with said pair of root rails; and a root groove definedbetween said pair of root rails.
 5. A fan according to claim 4characterized by:said pair of root rails having a wedge-shaped contour,said pair of root rails extending from said leading edge of said airfoilto said trailing edge thereof, said pair of root rails being tapered ina direction of decreasing cross-section from said leading edge to saidtrailing edge of said blade, and said pair of slot rails having awedge-shaped contour, said pair of slot rails extending from said frontside of said disk to said rear side thereof, said pair of slot railsbeing tapered in a direction of increasing cross-section from said frontside to said rear side of said fan disk.
 6. The fan according to claim 4or 5 characterized by a slot groove defined between said pair of slotrails for locating high hoop stresses radially inwardly therefrom.